In-flight icing is a critical technical issue for aircraft safety and, in particular, the droplet impingement areas on aircraft surfaces must be investigated for anti-/de-icing devices. As a step toward the prediction of droplet impingement on aircraft, an Eulerian-based droplet impingement code that provides collection efficiency for air flows around an airfoil containing water droplets is developed. A computational fluid dynamics (CFD) solver was also developed to solve the clean airflow. Then, a proper orthogonal decomposition (POD) method, a reduced order model (ROM), that optimally captures the energy content from a large multi-dimensional data set is utilized to efficiently predict the collection efficiency and ice accretion shapes on an airfoil following the mean volume diameter, liquid water contents and angle of attacks. As a result it is shown that the collection efficiency and ice shapes were in good agreement with the simulated and predicted results.
This paper describes a shape optimization study to maximize the range of a guided missile. To design a guided missile having maximum range, a shape optimization system is incorporated with a trajectory analysis program and an optimization technique. In particular, trajectory-dependent aerodynamic coefficients are fully considered. In the trajectory analysis step, a component buildup method is directly connected to the equation of motion to calculate aerodynamic coefficients at every time step. In the optimization step, a real-coded adaptive range genetic algorithm is adopted to determine the optimal shape of the global maximum range. The shape optimization system of a guided missile can maximize the range of the missile and yield the optimal shapes of canards and tailfins. Finally, the effects of trajectory-dependent aerodynamic coefficients, guidance, and control on the range of a missile are illustrated.= Mach number = angle of attack, rad c = canards deflection angle, rad
This paper describes a research of a shape optimization study to maximize a range of a guided missile with canards and tailfins. To design a guided missile for the maximum range, a shape optimization system is incorporated with a trajectory analysis and an optimization technique. In the trajectory analysis part, a component build-up method is directly connected to the equation of motion to calculate aerodynamic coefficients at every time step. In the optimization part, real coded adaptive range genetic algorithm was adopted to find out an optimum shape of the global maximum range. The shape optimization system of a guided missile for the maximum range can maximize the range of a guided missile and yield the optimum shape of canards and tailfins. The analysis results confirmed that the optimum shape thus derived extended the range of the base shape by 5.8% for the unguided case and by 21.4% for the guided case.
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